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IRIS G115E / TUTOR T.1, Flight Manual

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IRIS G115E / TUTOR T.1 Flight Manual Download Page 35

I A P   2 0 2 1 . 0 0 1 - A F M   /  

I R I S   G 1 1 5 E   /   T U T O R   T . 1  

        P a g e

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35 

 

FOR SIMULATION PURPOSES ONLY 

 

INSTRUMENTATION 

Introduction 

A pitot-static system supplies an airspeed indicator (ASI), both altimeters, and 
a vertical speed indicator (VSI). An alternate static system is also provided in 
the event of primary system failure.  

The attitude indicators (AI) and turn-and-slip indicator are electrically driven 
and are powered from separate busbars.  

Also fitted are various engine instruments and an accelerometer, standby 
magnetic compass and chronometer. 

Manifold Pressure / Fuel Flow Indicator 

 

A combined gauge shows manifold pressure on the upper scale graduated 
in inches of mercury (IN HG) from 10 to 35 and traversed by a pointer marked 
M. Fuel flow is indicated by a pointer marked F on the lower scale and is 
calibrated in litres per hour. 

 

 

Summary of Contents for G115E / TUTOR T.1

Page 1: ...FOR OFFICIAL USE ONLY AIR PUBLICATION 2021 001 AFM FLIGHT MANUAL IRIS G115E TUTOR T 1 Original Date of Issue 21st August 2021 Software Version V2 0 20210821 1814 ...

Page 2: ... 1 product by IRIS Simulations Pty Ltd for both Microsoft Flight Simulator Under NO circumstances is it intended to replace any form of real world training materials The intended use is for educational and entertainment purposes Should you require use for commercial or military applications please contact admin irissimulations com au to discuss your particular requirements OPERATING INSTRUCTIONS T...

Page 3: ...AND NOTES The following definitions apply to Warnings Cautions and Notes found throughout the manual WARNING Operating procedures techniques etc which may result in personal injury or loss of life if not carefully followed For the purposes of this product this would mean the end of the simulation session CAUTION Operating procedures techniques etc which may result in damage to equipment if not car...

Page 4: ...otherwise stated PROCEDURAL STEPS All procedures and checklists items are numbered sequentially with Arabic numerals USE OF THE FLIGHT MANUAL The use the Flight Manual correctly it is essential to understand the division of the manual into its sections and the subsequent division of the sections Each section has a table of contents and best use will be obtained from the Manual by becoming familiar...

Page 5: ...R I S G 1 1 5 E T U T O R T 1 P a g e 5 FOR SIMULATION PURPOSES ONLY TABLE OF CONTENTS Page No SECTION 1 DESCRIPTION AND OPERATION 6 SECTION 2 NORMAL PROCEDURES 44 SECTION 3 OPERATING LIMITATIONS 62 APPENDIX 1 PERFORMANCE DATA 66 ...

Page 6: ...APTER 1 DESCRIPTION AND OPERATION GENERAL THE AIRCRAFT 9 Introduction 9 Gross Weight 10 Cockpit Arrangement 10 Principle Dimensions Statistics 11 Engine 12 Ignition System 14 Electrical System 14 GENERAL EQUIPMENT 16 Introduction 16 Elevators 16 Ailerons 17 Rudder 17 Flaps 17 Stall Warning System 17 Landing Gear 18 Brakes 18 Air Conditioning 19 Accessibility 19 ...

Page 7: ... AIRCRAFT LIGHTING 21 External Lighting 21 Internal Lighting 21 COMMUNICATION EQUIPMENT 22 Bendix King KMA 26 Audio Communication System 22 Bendix King KTR 909 UHF Radio 23 Bendix King KX 155A VHF Radio 24 Bendix King KT 73 Transponder 24 NAVIGATION EQUIPMENT 25 Bendix King KX 155A Navigation Radio 25 Bendix King KN 53 Navigation Radio 27 Bendix King KN 63 DME 28 Bendix King KCS 55A Horizontal Sit...

Page 8: ...tor 36 Cylinder Head Temperature Fuel Pressure Indicator 36 Oil Temperature and Pressure 37 Exhaust Gas Temperature Outside Air Temperature 37 Volts and Amps Indicator 38 Fuel Quantity Indicator 38 Airspeed Indicator 39 Altimeter 39 Vertical Speed Indicator 40 Attitude Indicator 40 Turn and Slip Indicator 41 Accelerometer 42 Standby Magnetic Compass 42 Chronometer 43 ...

Page 9: ...t consists of a semi monocoque fuselage with a cantilevered wing conventional empennage and it is constructed mainly from carbon fibre reinforced plastic CRP The composite structure is protected from moisture and ultra violet radiation by a polyester gelcoat acrylic lacquer and an electro conductive filler This provides lightning strike protection and enables static electricity to be safely discha...

Page 10: ...pounds These weights shall not be used for computing aircraft performance or for any type of operation Refer to Section 3 Operating Limitations for take off and landing weights Cockpit Arrangement IRIS G115E Tutor T 1 Instrument Panel The cockpits are in a side by side arrangement with the instructor pilot sitting in the right seat with the student in the left Solo flight is conducted from the rig...

Page 11: ...oil NACA 64010 Span 3 50m2 Area 2 72m2 Elevator surface area 0 86m2 Fin Aerofoil NACA 64009 Area 1 69m2 Rudder Area 0 64m2 Undercarriage Wheel track 2 56m Wheel base 1 61m Nose wheel 500 5 6 PR Main wheels 15 x 6 00 6 Power Plant Engine Textron Lycoming AEIO 360 B1F Type 4 cylinder horizontally opposed air cooled direct drive fuel injected engine Displacement 361 0 cubic inches Rated power 180 HP ...

Page 12: ...ng tank capacity 2 x 75 litres Collector tank capacity 5 4 litres Useable fuel 143 litres Landing Gear Type Tricycle non retractable Main wheel pressure 44 PSI 3 bar Nose wheel pressure 36 PSI 2 5 bar Nose wheel steering range 47deg brake assisted Electrical System Generator 28 volt nominal 35 amp Battery 24 volt 10 ampere hour lead acid ...

Page 13: ...nd then to the exterior via two pipes below the cowling The starboard expansion chamber has a heater jacket in which air warmed by the exhaust gases is available for cockpit and windscreen heating The electric starter takes power from the main busbar Power is supplied through a starter relay operated by the starter button A STARTER caption on the Caution Warning Panel which when illuminated indica...

Page 14: ...top the engine and reload the aircraft ELECTRICAL SYSTEM The aircraft uses a DC electrical system powered by either a 24 volt battery or an engine driven generator of 28 volt output The power is distributed through 4 busbars and most systems are protected by circuit breakers The circuit breakers are arranged in busbar groups in the cockpit Battery A 24 volt 13 6 amp per hour battery is located beh...

Page 15: ...otect the system Main Busbar The Main busbar is supplied with power from the battery or the generator or an external supply on the ground The Main busbar distributes power to the Essential busbar Avionics 1 busbar Avionics 2 busbar and other services directly Essential Busbar The Essential busbar provides power to the minimum services deemed essential for the safe recovery of the aircraft Avionics...

Page 16: ...g controls consisting of a control column and rudder pedals at each crew position The head of the column is fitted with a press to transmit PTT switch The control surfaces are mass and aerodynamically balanced and comprise of Ailerons Differential and Frise ailerons extend over the outer third of each wing trailing edge Elevators Elevators extend over the whole width of the tailplane trailing edge...

Page 17: ...el top to the right moves the pedals rearwards Attached to the top of each rudder is a wheel brake toe pad The rudder cannot be trimmed in flight but it has a fixed tab which can be adjusted on the ground Flaps A simple flap is fitted to the trailing edge of each wing between the aileron and the wing root walkway The two flaps are interconnected by push pull rods and operated by a single electrica...

Page 18: ...tted with hydraulic disc brakes and each pilot has a set of toe brake pedals Pressure is generated by the pilot pushing on the top of the rudder pedal The left brake is controlled by the left brake pedal and the right brake is controlled by the right brake pedal The brakes are progressive The harder you press the harder the brakes are applied Take care not to lock the wheel or the tyre could be da...

Page 19: ...opy consists of a frame which slides on 3 rails and includes an overhead latch to lock it closed When closed a pin engages at the front and rear of each side rail to hold the canopy down Furnishing The aircraft has two seats each with a cushion and safety harness The seats are not adjustable but sitting position may be varied by the use of cushions of differing thickness Each occupant may wear a b...

Page 20: ...eration and the mounting allows removal with one hand The unit is discharged by squeezing the trigger on the operating head It is primarily intended for use after a crash landing however if it is used in flight due to the noxious nature of Halon the cockpit should be ventilated immediately after operating the extinguisher and medical advice sought on landing Escape Hammer A combined escape hammer ...

Page 21: ... on the port side and green on the starboard The wingtip units also incorporates rear facing white navigation lights Anti Collision Lights A red anti collision light is on the lower fuselage Strobe Lighting High intensity white strobe lights are fitted at each wing tip Anti dazzle plates are incorporated into the fittings Landing Light A landing light is installed in the lower part of the engine c...

Page 22: ...luminates on activation Selecting the mute switch reduces the volume of all incoming audio signals by 6 dB thus broadcasts may still be heard but at a reduced level The Mute does not affect the outgoing audio signal Deselecting mute returns all volumes to the pre set level Power is supplied to all the units via the Avionics 1 and 2 Busbars and associated circuit breakers Lighting levels on the uni...

Page 23: ... aid Pushing a button selects the audio source pushing it again deselects it Of the 10 selectable sources COM 3 ADF and AUX are unavailable MONI will play back random radio chatter Bendix King KTR 909 UHF Radio The KTR 909 UHF transceiver provides two way voice communications over the frequency range available in the simulation Manual frequency selection is achieved using the concentric rotary con...

Page 24: ...s A clockwise rotation increases the frequency and rotation of the control beyond the frequency limits wraps the display around to the other end of the frequency band Active and Pre set modes are not simulated in this device Bendix King KT 73 Transponder The KT 73 is a panel mounted Transponder with Mode S Level 2 Datalink which offers a comprehensive functional and safety capability It incorporat...

Page 25: ...55A NAV COMM transceiver a KMA 26 with Marker receiver and a KN 63 digital DME receiver The information from these units is displayed on a KCS 55A Horizontal Situation Indicator HSI and a KI 204 VOR ILS Glideslope indicator known as an Omni Bearing Selector OBS Bendix King KX155A Navigation Radio The NAV facility of the KX 155A KX 165A NAV COMM transceiver is a sophisticated unit capable of digita...

Page 26: ...ontrols changes the frequency in the Active display Depressing the NAV frequency transfer button will place the Active frequency in blind storage and transfer the Standby frequency to the Active window When the Active window is tuned to a VOR frequency the Standby frequency area is replaced by a 3 digit OBS display The OBS course value is tied to the NAV2 Indicator on the Left side of the instrume...

Page 27: ... MHz in 50 KHz increments DME channelling is provided for the KN 63 digital DME receiver Rotating the ON Off Vol control clockwise turns on the unit NAV voice may be heard via the NAV 1 function on the ACS is pressed illuminated Display brightness is automatically controlled Rotating the concentric frequency control positioned on the right of the unit selects a frequency in the STBY display The ou...

Page 28: ...n of a GPS flight plan Once the unit has locked on to the selected station DME distance will be displayed in 0 1 NM increments up to 99 9 NM then in increments of 1 NM to 389 NM Distance is calculated by electronically converting the elapsed time for signals to travel to and from the ground station Groundspeed calculations are based on the rate of change of DME distance Time to station is calculat...

Page 29: ...pe for stabilization of the system and the HSI display itself Track information from the DGPS may also be displayed when selected using the NAV1 GPS button to the right of the DME unit however the button will always default to NAV1 if an ILS frequency is selected on the NAV1 receiver The display unit for the HSI contains flags and indicators to present a wide variety of information The various com...

Page 30: ...position relative to the selected course Each dot on the deviation scale represents 2 of deviation left or right of the selected VOR or DGPS course When tuned to an ILS frequency the deviation is per dot Heading Select Bug This movable marker on the perimeter of the display is used to mark the desired heading It is set by rotating the heading select knob To From Indicator This is a white triangle ...

Page 31: ...t the VOR localizer and glide path deviation bars the To From indicator and the NAV flag will continue to give correct information NAV Warning Flag This red flag appears in the upper left quadrant whenever an unusable VOR localizer signal is being received or the NAV receiver unit is not turned on NAV GPS Selector The NAV GPS button directs either NAV 1 or GPS information to the HSI selected cours...

Page 32: ...the aircraft computed position Operation with the ground station provides the differential mode DGPS NOTE This unit does NOT allow the direct input of flight plan data It is a data display device and as such the FSX P3D Flight Planner tool or an external flight planning software may be required for flight plan creation CAUTION Due to the nature of the unit and programming limitations at the time o...

Page 33: ...rport positions and shows the following information for each on the display Name Bearing to TO NAV point Distance DIS from present position to NAV point NM Navigation Display Mode This contains all the information necessary to navigate to a pre determined waypoint At the uppermost element of the screen is the waypoint identifier and unit mode i e NAV On the main screen from left to right top to bo...

Page 34: ...t Destination Airport Mode The Destination Airport mode displays required information in relation to the destination airport on the loaded DGPS flight plan At the uppermost element of the screen is the destination airport name identifier and navigation mode i e NAV On the main screen from top to bottom are the following elements ICAO ICAO Code of the destination airport NAME Name of the destinatio...

Page 35: ...ilure The attitude indicators AI and turn and slip indicator are electrically driven and are powered from separate busbars Also fitted are various engine instruments and an accelerometer standby magnetic compass and chronometer Manifold Pressure Fuel Flow Indicator A combined gauge shows manifold pressure on the upper scale graduated in inches of mercury IN HG from 10 to 35 and traversed by a poin...

Page 36: ... graduation when it is ready to accept RPM signals Engine start before the indicator shows zero will result in either no or incorrect RPM indication Cylinder Head Temperature Fuel Pressure Indicator A combined gauge shows Cylinder Head Temperature CHT on the right hand side marked 0 C to 300 C A red radial line is at 260 C an amber arc covers the range 0 C to 65 C and a green arc covers 65 C to 26...

Page 37: ...dial line at 120 C an amber arc covering 40 C to 60 C and a green arc covering 60 C to 120 C Oil pressure is indicated on a scale graduated 0 to 120 psi with red radial lines at 25 and 100 psi amber arcs covering 25 to 60 and 90 to 100 psi and a green arc covering 60 to 90 psi Exhaust Gas Temperature Outside Air Temperature A combined gauge displays EGT on the left hand side on a scale marked 1200...

Page 38: ...s than 25 0 5 volts An ammeter amp indicator shows the flow from the battery or external supply to the busbars a negative charge shows battery discharge and a positive charge shows the generator charging the battery Fuel Quantity Indicator The fuel gauge float sensor in each wing is at maximum travel with 63 litres in the tank hence the extra 12 litres in each main tank is ungauged More than 60 li...

Page 39: ...red radial line indicating VNE and a blue radial line at the recommended sea level climbing speed Altimeter The altimeters on each side of the instrument panel are identical Altitude is shown on the dial by 3 pointers the longest pointer indicates hundreds of feet the second slightly shorter diamond shaped pointer indicates thousands of feet and the shortest pointer indicates tens of thousands of ...

Page 40: ...ide of the instrument panel are AIM 1100 or Mikrotechna LUN 1241 series electrically driven instruments powered from separate busbars The primary instrument the starboard AI is powered from the Essential busbar and the other the alternate instrument is powered from the Avionics II busbar Each gyroscope is connected to a blind marked with a horizon line and lines representing pitch values of 5 10 1...

Page 41: ...ULL FOR QUICK ERECT This aligns the gyro to the zero pitch and bank attitude relative to the instrument case by means of mechanical cams thus the aircraft must be in straight and level flight at 100 kts before erecting the instrument The instrument remains accurate up to 85 of pitch and through 360 of roll Turn and Slip Indicator This is a ball and pointer instrument in which a ball moves about th...

Page 42: ...ght Two auxiliary pointers show the greatest positive and negative accelerations achieved since the instrument was reset A PUSH TO SET knob on the instrument allows the auxiliary pointers to be reset to 1g Standby Magnetic Compass The compass is a permanent bar liquid damped instrument mounted centrally on the coaming The markings are at 5 intervals and a range of 60 is visible in the window Illum...

Page 43: ...ULATION PURPOSES ONLY Chronometer The chronometer is powered electrically The clock displays the time with a conventional 2 hand 12 hour display Some clocks have a 60 seconds display on an internal scale and the date displayed in a small aperture near to the 5 o clock position ...

Page 44: ...ARATION FOR FLIGHT 48 Before Starting 48 Starting the Engine 48 After Starting 49 Taxiing 49 Testing the Engine 50 CHAPTER 2 HANDLING IN FLIGHT 51 Take Off 51 Climbing 51 General Flying 52 Flight in Icing Conditions 52 Flight in Turbulent Conditions 52 Engine Handling 52 Mixture Control 53 Descending 54 Stalling 55 Spinning 56 Aerobatics 58 Simulated Emergencies 60 ...

Page 45: ... g e 45 FOR SIMULATION PURPOSES ONLY TABLE OF CONTENTS cont Page No CHAPTER 3 CIRCUIT AND LANDING PROCEDURES 61 Approach Procedures 61 Circuit Procedures 61 Landing 61 Roller Landings 62 Going Around 62 Braking Techniques 62 Nose Wheel Shimmy 62 After Landing 63 ...

Page 46: ...edals to a comfortable position Fasten harnesses and ensure that if solo the harness for the LH seat is also fastened Set the parking brake by first sliding the parking brake lever to the SET position and pressing both brake pedals until full resistance is felt One moderate application of pressure is normally sufficient but further pressure can be applied to the wheel brakes at any time by pressin...

Page 47: ...l cause excessive wear to a cold engine After Starting Carry out the After Starting Checks The ignition check is achieved by moving the ignition switch from BOTH to R back to BOTH from BOTH to L and finally back to BOTH The RPM should drop slightly on R or L alone but the engine should not stop If the engine cuts out then a dead magneto exists If the RPM does not reduce when selecting R and L then...

Page 48: ...ccordance with the checklists with the nose wheel straight and keeping the control column in the central position Keep the ground operation of the engine at high power to a minimum to avoid overheating When exercising the propeller RPM control ensure that the lever is operated throughout its range and that the RPM changes by 500 but no more This allows maximum circulation of the oil between the en...

Page 49: ...given to abandoning the take off and having the fault investigated For take off on a grass runway reduce the load on the nose wheel as early as possible In crosswind conditions initially up to full aileron may be required to prevent the into wind wing from rising After take off hold the aircraft in a shallow climb and allow the speed to increase to climbing speed At 80 kts and a minimum of 150 ft ...

Page 50: ... reducing below normal limits Prolonged flight in this regime will progressively damage the engine and may eventually result in mechanical failure Therefore if the oil pressure does reduce below normal limits balanced flight must be resumed within 10 seconds Flight in Icing Conditions The IRIS G115E Tutor T 1 has no airframe or propeller de icing or anti icing protection and only limited engine de...

Page 51: ...forward enriches the mixture and increases fuel flow and vice versa Moving the lever aft to the fully lean position will shut off fuel completely causing the engine to stop The three mixture settings relevant to Tutor operations are Best Power Mixture BPM Best Economy Mixture BEM and Endurance BPM This setting is used for almost all training exercises flown on the Tutor Before take off with the ai...

Page 52: ...ing speed is 75 kts In still air with the throttle closed the clean aircraft travels approximately 1 25 nm per 1000 ft height loss with the RPM control set to HIGH and 1 5 nm per 1000 ft with LOW RPM set CHT reduces quickly during a closed throttle descent and the spark plugs rapidly become contaminated with oil Power response may then be poor and engine damage may occur Following a simulated engi...

Page 53: ...e stalling speeds at an operating weight of 990 kg for both Normal and Alternate static sources are Aircraft Configuration Speed Knots Normal Alternate Power Off Flaps UP 52 52 Power Off Flaps TAKE OFF 50 49 Power Off Flaps LAND 49 48 Power Off Flaps FULL 49 45 Power On Flaps LAND Typical Approach Configuration 52 47 Power On Flaps FULL 52 47 The stall in the turn is indicated by moderate buffet a...

Page 54: ...pin The aircraft will initially pitch up and roll and then after about 360 of roll the nose of the aircraft will drop into a full spin The normal spin is maintained by holding the control column fully back with the ailerons central and full rudder deflection in the direction of spin The spin will stabilise between 60kts and 86kts with each turn taking up to 3 seconds Recovery There is only one rec...

Page 55: ...t be taken within this parameter and initiated as soon as possible after recognition of departure Centralising all flying controls promptly produces a successful recovery Alternative Emergency Spin Recovery To recover from a spin the Tutor Full Spin Recovery should be used However if having completed the Full Spin Recovery a pilot finds himself disorientated or the aircraft does not recover as he ...

Page 56: ... 130 kts Knife Edge Flight 135 kts Noddy Stall Turn 140 kts Lazy Eight 130 kts Vertical Roll 150 kts Loop 130 kts Outside Loop erect 70 kts Outside Turn 130 kts Outside Loop inverted 150 kts Slow Roll 130 kts Reverse Stall Turn 140 kts Stall Turn 120 kts Rolling Turn 130 kts Quarter Clover 120 kts Dynamic Spinning flick entry max IAS 100 kts Derry Turn 120 kts Dynamic Spin The dynamic spin or flic...

Page 57: ...ion commences If a snap roll through more than 180 degrees is required full rudder in the direction of roll should be maintained but the CC should be moved forward to a more neutral position as sustained rearward deflection can lead to a high drag situation and may impose undue loading on the fuselage During autorotation the following control inputs accelerate the roll rate Aileron in the directio...

Page 58: ... to ensure that the aircraft is configured for landing in the event of actual engine failure in the latter stages of the approach or go around For this reason the PRE LANDING CHECKS with the exception of take off flap should be completed prior to reaching the Hi Key position In addition on the crosswind leg of the forced landing pattern an engine warm should be carried out If the CHT has fallen be...

Page 59: ...if considered necessary and fly the final approach at 70 kts On short finals start reducing the IAS with a small power reduction in time to achieve threshold speed as the runway threshold is crossed Landing The flare is commenced at a suitable height with backward movement of the control column and closure of the throttle The nose is pitched up at a rate to control the now reducing rate of descent...

Page 60: ... safely with FULL flap raise the flaps within the speed and height limitations and complete the After Take off Checks Braking Techniques As soon as the main wheels are on the ground lower the nose wheel to the runway Apply the wheel brakes gently at first to avoid locking a wheel it is difficult to detect if a wheel is locked from the cockpit Increase braking pressure as the groundspeed decreases ...

Page 61: ...eturning to BOTH with RPM recovery The procedure is then repeated selecting L Finally briefly select OFF and return to BOTH observing that the engine would dead cut i e stop with OFF selected When shutdown is complete release the parking brake if appropriate and vacate the aircraft WARNING The ignition shutdown check must be completed thoroughly and not rushed particularly the OFF dead cut check F...

Page 62: ...age No AIRFRAME 65 Maximum Speeds 65 Operating Limitations 65 Weight 65 Airfield Limitations 65 Arrester Gear Trampling 65 Negative G 65 Normal Acceleration 65 Limitations for Raising Flap 66 ENGINE LIMITATIONS 67 RPM 67 Maximum Permitted MP in HG 67 Magneto Drop at 2000 RPM 67 Cylinder Head Temperature 67 Oil Pressure 67 Oil Temperature 67 Fuel 67 ...

Page 63: ...th canopy fully open 80 kts Maximum speed with canopy in vent position emergency only 100 kts Operating Limitations Maximum altitude FL 100 Minimum OAT at MSL 10 C Aerobatics and spinning are prohibited when baggage is carried Weight Take off and Landing 990 kg In baggage compartment 55 kg Airfield Limitations Maximum wind speed 40 kts Maximum crosswind 25 kts Arrester Gear Trampling Supported cab...

Page 64: ...G 1 1 5 E T U T O R T 1 P a g e 64 FOR SIMULATION PURPOSES ONLY Limitations for Raising Flap LAND FULL to TAKE OFF 70 kts min TAKE OFF to UP Above 150 ft AGL 80 kts min NOTE The quoted speeds may be reduced by 5 kts above FL 50 5000 ft ...

Page 65: ...50 RPM Maximum drop on each magneto 175 RPM Maximum difference between RPM on individual magnetos 50 RPM Cylinder Gear Temperature Minimum during flight 65 C Maximum at full throttle 260 C Maximum at BPM Cruise 225 C Maximum at BEM Cruise 205 C Oil Pressure Maximum during start and warm up 100 PSI Minimum at ground idle 25 PSI Normal operating range 60 to 90 PSI Oil Temperature Maximum permitted 1...

Page 66: ...itude ft IAS Kts Indicated Fuel litres Range NM Time Mins SL 100 120 294 176 5 4000 ft 284 157 9 8000 ft 279 148 5 SL 100 80 181 109 0 4000 ft 172 97 3 8000 ft 169 90 0 SL 100 40 62 37 5 4000 ft 59 33 3 8000 ft 57 31 5 Endurance ISA Flaps UP Endurance is hours remaining until tanks dry Altitude ft IAS Kts RPM Fuel Flow Litres hr Indicated Fuel Litres Endurance Hours SL to 10000 ft 80 1800 20 120 6...

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